Aeroplane



J. ZURUK-ZURINSKY.

AEROPLANE.

APPLICATION FILED FEB-19.1920.

1,381,611 PatentedJune 14, 1921.

3SHEETS-SHEET 1.

J. ZURUK-ZURINSKY.

AEROPLANE.

APPLICATION FILED FEB. 19, 1920.

1,381,61 1 Patented June 14, 1921.

3 SHEETSSHEE'I 2.

WWNEN' NvEm-mR TfiI/ww l J. ZURUK-ZURINSKY.

AEROPLANE.

APPLICATION FILED FEB-19,1920.

3 SHEETS-SHEET 3.

INVENTOR @WZM WITNEss Patented June 14, 1921.

UNITED STATES PATENT OFFICE.

JOHN ZURUK-ZU'RINSKY, F MCKEESPORT, PENNSYLVANIA.

AEROIPLANE.

Specification of Letters Patent.

Patented June 14, 1921.

Application filed February 19, 1920. Serial No. 359,895.

, is a specification.

This invention relates to new and useful improvements in aeroplanes,particularly of the biplane type, and the object thereof is to providein an aerial vessel of the type stated, in the manner as hereinafter setforth, stabilizing means to prevent dangerous tipping, swerving, andoverturning of the vessel, and to reestablish its balance and maintainits equilibrium, even when disturbed, during the operation thereof, byuntoward wind, air, and weather conditions,-

under such conditions providing for the efiicienttravel of the vesseland reducing to a minimum the liability of accident.- to the aviator.

Further objects of the invention are to" provide an aerial vessel of thecharacter described which is comparatively simple in its constructionand arrangement, strong, durable and efficient in its use, andinexpensive to manufacture.

To the accomplishment of these and such other objects as may hereinafterappear, the invention consists of the novel construction, combinationand arrangement of parts herein specifically described and illustratedin the accompanying. drawings wherein is shown an embodiment of theinvention, but it is to be understood that the device shown is merelyillustrative and that a various changes in the form, proportion andminor details of construction may be resorted to, Without departing fromthe principle or sacrificing any of the advantages of the invention,which come within the scope of the claims hereunto appended.

In the drawings forming a portion of this specification and wherein likenumerals ofreference designate corresponding parts throughout theseveral views:

Figure 1 is a side elevation of the biplane in accordance with thisinvention.

Figs. 2 and 2 are top plan views of respective portions thereof.

Fig. 3 is a front elevation of the aeroplane.

Referring to the drawings in detail 1 indicates the tonneau or main body1 of the aeroplane, which may be of any suitable construction or form,and comprises the power plant 2, and compartments 3 and 4 for pilot andpassenger, respectively. A tractor propeller 5 operates at the forwardend of the main body 1 and the products of combustion from the engineare exhausted through the rearwardly extending pipe 6, which ispositioned well toward the top of the main body 1. 3

An upper plane 7 and a lower plane 8 are rigidly secured together inspaced relation with respect to each other by the central. invertedV-shaped stanchions 9, the intermediate pairs of stanchions 10 and 11,respectively, and by the end mast stanchions 12 and 13, which arearranged between the planes 7 and 8, near the ends thereof, and each ofwhich is disposed forwardly with respect to the longitudinal center ofthe planes. The stanchions 9,10 and 11 are suitably braced by the gu'ywires 14, and the stanchions 12, 13 are braced by the guy wires 14 and14'.

The lower plane 8 is embodied in the main body 1, which latter isrigidly secured in the plane structure by being fixedly attached to thestanchions 9.

Each rear corner of the upper plane 7 is cut away, as at 15. so that theedge thereof will extend transversely, longitudinally and forwardly onan inclination, with respect to the plane 7 The transverse portion ofthe edge merges into the longitudinal portion and the latter merges intothe inclined portion, the latter terminates at the end of the plane 7Arranged within the cut-away portion 15 is an auxiliary wing 16,hingedly connected. as at 17, to the longitudinal part of the edge ofthe cut-away portion 15. Each of the wings 16 consists of a rectangularbody of greater length than the length of the cut-away portion 1'5 andprojects beyond the end of the plane 7, and at the outer part of therectangular body of the wing 16, the said body is formed with atriangular extension whichopposes the inclined part of the edge of thecut-away portion 15.

Each of the auxiliary wings 16 is operated by a pair of flexible members19 and 20, both attached to the lower face of the wing, the former nearthe rear end thereof and the latter at the front end of the extension18, thereby permitting the operation of the wing on the hingedconnection with the upper plane? when the flexible members 19 and 20 aremanipulated by the pilot. The flexible members 19 and 20 extendvertically from. each wing to the lower plane 8, and through the latterto respective levers 21 and 22, operatively mounted on the shaft 23 inthe pilots compartment 4. The operation of the. wings 16 is adapted toprevent overturning sidewiseand to assist in the steering of'thebiplane. As but a single end stanchionis employed, and which is disposedforwardl'y with respect to the longitudinal center'of, the plane 7,provision is made-whereby a wide rectangular body of the wing 16 can beemployed, under such conditions obtaining a greater working surface forthe wing, than if the ends of the planes 7 and -8"we;re braced andsupported by two end stanchions', as if these two latter were employedthe body of the wing 16 would be compelled to be narrow.

As clearly shown in Fig. 2, of the ,drawings, the lower plane 8 inclinesrearwardly from its center toward each end thereof and projects beyondthe rear edge of the upper plane 7. This construction of the lower plane8 is primarily provided to augment the efiiciency of the operation ofthe wings 16 on the upper plane-7, as it permits amore direct action ofthe air against the said wings 16 than if the said lower plane 8extended farther forward, without detracting from the sustainingcapacity of the said plane.

The fuselage 24, is provided at its rear with a supporting bracket 24,which is secured centrally thereof to the fuselage 24, has a rearstraight edge, and each side edge formed with a rearwardly and outwardlyinclined portion and a rearwardly and inwardly inclined portion. Theoutwardly inclined portion of the side edge of the bracket 24' is ofmaterially greater length than the inwardly inclined portion of saidedge. The bracket 24 is provided as a carrier for the rudder 25. Thelatter is horizontally disposed and is formed at its front with acutaway portion into which extends the bracket 24, and the rudder 25 ishinged to the bracket 24. The rudder 25 has a pair of outwardly inclinededges which form continuations of the outwardly inclined edges of thebracket 24. The rear edge of the rudder 25, inclines forwardly andoutwardly from its center toward each end. The side edges of the rudder25 are straight. Flexible members 27 are employed for operating therudder 25. The fuselage 24 is provided at its rear with a verticallyextending supporting bracket 25 to which the vertical rear rudder 26 ishinged, the latter overlaps the bracket 25' and is operated by theflexible members 28.

The members 27 and 28 pass from their respective rudders forwardlythrough the inclosedportion of the fuselage 24 and connect to respectiveoperating levers 29 and 30 which are carried by the shaft 23 in thepilots compartment '4.

The lower portion of the fuselage 24, atthe rear thereof, see Fig. 1, ofthe drawings, is formed with an enlarged tri-angular shaped opening orpassage 32, with the framing at that part of the fuselage 24 exposed.This construction of fuselage offers less re sistance to the crosscurrents of air, thereby preventing lateral swerving of the aeroplaneand assisting in maintaining its equilibrium while operating in untowardair, wind, and weather conditions. The inclosed lower portion 31, of thefuselage 24, provides an ideal location for the fuel tankv 33, beingremotely removed from the power plant 2, thereby rendering the aerialvehicle less liable to fire in case of accident. The portion 31 of thefuselage 24, which is inclosed provides sufficient support when restingon the water, which would not be the case if such portion 31 wasconstructed solely of the frame work of the fuselage 24.

The lower portions of the forward inverted V-shaped central stanchion 9form the supports 34 for the landing chassis 35. Each of the supports 34is provided with a spring shock absorber 36 to counteract the landingimpact of the aeroplane. The tail of the aeroplane is provided with theusual rearwardly extending and resiliently mounted landing leg 37 Thesupports 34 are rigidly braced by the rearwardly extending bracingmembers 38.

Any desired type of landing chassis may be employed in connection withmy improved aeroplane, or same may be'provided with suitablesubstitution to permit of its use for starting or landing on water.

lVhat I claim is:

1. An aeroplane comprising a fuselage having the lower partof the rearthereof formed with an enlarged triangular shaped opening.

2. An aeroplane comprising a fuselage having the lower part of the rearthereof provided with an enlarged triangular shaped opening, and thatpart of the fuselage below the forward part of said opening beinginclosed.

3. An aeroplane comprising a fuselage having the lower part of the rearthereof pro vided with an enlarged triangular shaped opening and thatpart of the fuselage below the forward part of said opening being incloslgd and providing a chamber for a fuel tan 4. An aeroplanecomprising a fuselage, a horizontally disposed bracket secured centralthereof to the rear end of the fuselage and having its side edges eachinclined rearwardly and outwardly and rearwardly and inwardly. saidoutwardly inclined portion of greater length than the inwardly inclinedportion of the side edge, and a horizontally disposed rudder having itsforward portion cut away to abut the inwardly inclined portion of theside edges of the bracket, said rudder further having inclined edgesforming a continuation of the outwardly inclined edges of said bracket,and said rudder further having its rear edge inclined forwardly andoutwardly from its center toward each end of said edge.

5. An aeroplane comprising an upper and a lower plane, end stanchions,each of said stanchions arranged between said planes near the ends ofthe latter and disposed forwardly with respect to the longitudinalcenter of the planes, and said upper plane having each rear cornerthereof to provide an edge to extend transversely, longitudinally and atan outward and forward inclination with respect to said plane, and anauxiliary wing mounted in each cut-away portion and conforming incontour to the shape of the said cutaway portion and further hinged tothe longitudinal portion of said edge.

6. An aeroplane comprising an upper plane having each rear cornerthereof cut away to provide an edge having portions to extendtransversely of the plane, longitudinally of the plane and at an outwardand forward inclination with respect to the plane, said transverseportion merging into said longitudinal portion and the latter merginginto the inclined portion, the latter terminating at the end of theplane, and an aileron mounted in and of the same contour as the cut-awayportion and projecting beyond the end of the plane.

7. An aeroplane comprising an upper and a lower plane, an invertedV-shaped stanchion interposed between and secured to said planes, pairsof intermediate vertically disposed stanchions interposed between andsecured to said planes, and an end stanchion interposed between andsecured to the planes near the outer ends thereof, each of said endstanchions arranged forwardly with respect to the longitudinal center ofthe planes.

In testimony whereof I afiix my signature.

JOHN ZURUK-ZURIN SKY.

